Continuous Combustion Chamber TRIZ Cases

A cryogenic heat exchanger cools compressed air to below -30°F for engine component testing.

Two centrifugal pumps in series handle distinct fuel flow rates to maintain constant efficiency across engine speeds.

Integral additive assembly merges burner seal and heat shield to optimize opening edge geometry for fuel-air mixing.

Sequential hood replacement maintains vacuum conditions and reduces downtime caused by thermal degradation.

A gas turbine separates fuel into rich and lean streams to optimize sequential combustion stability across varying load conditions.

Segmented flow guide members distribute compressed air uniformly to reduce pressure loss from swirls in gas turbine combustors.

A turbomachine fuel injection system positions a nozzle near the spark plug to generate a wide-angle fuel pool.

Tapered outlet ring promotes swirling flow to uniformize fuel concentration, reducing high-temperature retention time and NOx generation.

Micro-flameholders induce transverse accelerations to promote Rayleigh-Taylor instability and interpenetration of reactants within combustors.

Sectorized annular sealing member fills radial clearance between end wall and shroud to prevent parasitic air leakage and combustion gas escape.

A modular injection head design merges swirler and fuel insert components to simplify assembly.

Segmented hanger assemblies with pivoting joints accommodate thermal expansion in gas turbine engines while simplifying installation.

Curved hourglass cooling pedestals expand surface area to enhance convective heat transfer in turbine engines.

A tunable resonator with adjustable plates absorbs acoustic pressure waves to suppress combustion dynamics.

A gas turbine combustor adjusts fuel flow between premixed and diffusion burners to manage flame conditions.

Embedded cooling channels activate upon wall breach to deliver targeted fluid flow, preventing thermal barrier coating spallation and extending component life.

Curved panel edges resolve sharp corner issues, ensuring reliable coating adherence and durability in high temperature gas turbine environments.

Prismatic injection nozzle with oblique intermediate walls deflects radiant heat away from fuel-air mixtures.

Inclined strut injection holes in a combustor nozzle create swirl flow, resolving non-uniform fuel-air mixing and reducing NOx emissions.

A dilution gas admixer controls inlet flow conditions in a sequential combustor arrangement.

Merging supply and purge circuits into one solenoid valve reduces manufacturing costs while maintaining combustion stability.

A gas turbine combustor wall assembly uses contoured support shell regions to direct cooling air through convergent passages between liner panels.

A trapped vortex reverse flow combustor design generates internal vortex flow to direct primary airflow backward through the combustion chamber.

Asymmetric streamlined bodies with right and left handed lobes dampen rotating thermoacoustic pulsations in gas turbine burners.

Asymmetric inclined flow passages jet air along the cover ring front surface to cool the component while maintaining flame stability.

An asymmetric airfoil turbulator eliminates stagnation zones and dust deposition while maintaining boundary layer tripping for efficient cooling.

Floating mounting with axial and radial springs accommodates thermal expansion of mixing tubes, reducing mechanical stresses in gas turbine fuel nozzles.

A delta wedge element inside a film cooling hole generates counter-rotating vortices to neutralize chimney vortices and reduce cooling air consumption.

Helmholtz resonators align with hot and cold combustor regions to optimize cooling airflow.

Layered manifold cavities shorten fuel paths to reduce waste heat loss and simplify piping complexity in gas turbine engines.

A fuel nozzle with contoured inner and outer walls accelerates oxidizer flow to create a forward stagnation point between the throat and exit plane.

An adjustable mixing housing arrangement with a bolt and wedge washer device enables precise concentric positioning of the flame tube.

Seal spacer segments lip seals axially to accommodate thermal growth and reduce fuel leakage between concentric tubes.

Water injection into the first combustion area cools the zone and reduces hydrogen reactivity, preventing flashback risks during retrofitting.

Multi-lobed dilution openings in a gas turbine combustor liner reduce wake formation and NOx emissions by improving lateral air mixing.

Additive manufacturing creates complex effusion cooling holes in gas turbine combustor liners.

Dual-conduit fuel delivery manages syngas and natural gas transitions while steam injection reduces NOx emissions.

Segmented resonator rings with shared walls simplify manufacturing and extend component lifespan by reducing machining complexity.

A film-cooled recess with a contoured step directs cooling fluid to delay mixing with hot combustion gas.

Radial feed arms extend from an annular manifold to deliver fuel through isolated flow passages toward combustion nozzles.

Segmenting the manifold into distinct circuits reduces assembly complexity while maintaining ignition reliability during startup.

A gas turbine fuel system diverts hydrogen to a burner and heat exchangers for preheating.

Segmented fuel circuits with electrically-controlled valves enable active patternation to mitigate combustor noise without adding mechanical hardware.

Inline injection through a lobed trailing edge generates vortices that mix fuel and air while reducing pressure losses in gas turbine combustion chambers.

Axial swirler applies non-uniform camber and thickness distributions to enhance fuel-air premixing while reducing pressure losses.

Overlapping combustor panels form spiral radial gaps that admit cooling air for film cooling on hot annular walls.

A turbine support hanger uses a pivoting collar and pin to accommodate thermal expansion between exhaust liner and duct.

An inclined surface on the inner cylinder of a turbine diffuser increases boundary layer velocity to prevent flow separation.